A cryogenic propellant tank is the common element of trans‐planetary transportation systems, in‐space storage depots, lunar landers, in‐space habitats/laboratories, ascent/descent, and launch vehicles. Lockheed Martin’s (LM) cryogenic tank approach integrates Friction Stir Welding (FSW) with thin‐gage aluminum monocoque structural design, common spin formed FSW domes and variable tank lengths to tailor the cryogenic tank from smaller stages, such as landers or ascent/descent stages, to very large on‐orbit or In Space Resource Utilization (ISRU) storage systems. Thin gage corrosion resistant steel (CRES) construction combined with normal fusion welding as used on LM’s Centaur has already been demonstrated to provide the highest cryogenic tank mass fraction (∼.90) for large scale, cryogenic propellant storage. However, current fusion welding technology is limited by the alloys that are considered weldable and typically achieves only 50% of the parent material ultimate strength at the weld joint. Preliminary LM technology development indicates that in certain aluminum alloys, the FSW joint retains up to 100% of the parent material ultimate strength at LH2 temperatures. Combining FSW and aluminum monocoque tank design would create a large scale cryogenic tank with a mass fraction in excess of the current industry standard and therefore is ideal for affordable, reliable, high capacity propellant storage required for all facets of space exploration.
Friction Stir Welded Thin Wall Cryogenic Tank Skins
SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2007: 11th Conf Thermophys.Applic.in Micrograv.; 24th Symp Space Nucl.Pwr.Propulsion; 5th Conf Hum/Robotic Techn & Vision Space Explor.; 5th Symp Space Coloniz.; 4th Symp New Frontrs & Future Con ; 2007 ; Albuquerque, New Mexico (USA)
AIP Conference Proceedings ; 880 , 1 ; 736-741
30.01.2007
6 pages
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
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